EP3061975A1 - Axial compressor with flow recirculation - Google Patents
Axial compressor with flow recirculation Download PDFInfo
- Publication number
- EP3061975A1 EP3061975A1 EP16155778.0A EP16155778A EP3061975A1 EP 3061975 A1 EP3061975 A1 EP 3061975A1 EP 16155778 A EP16155778 A EP 16155778A EP 3061975 A1 EP3061975 A1 EP 3061975A1
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- stator
- stage
- fluid
- compressor
- air
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- 239000012530 fluid Substances 0.000 claims abstract description 59
- 238000000034 method Methods 0.000 claims abstract description 34
- 230000003068 static effect Effects 0.000 claims description 46
- 238000011144 upstream manufacturing Methods 0.000 claims description 13
- 238000004891 communication Methods 0.000 claims description 12
- 238000002485 combustion reaction Methods 0.000 description 10
- 238000003466 welding Methods 0.000 description 5
- 239000000203 mixture Substances 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000005266 casting Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000013011 mating Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 230000011664 signaling Effects 0.000 description 1
- 230000002123 temporal effect Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0238—Details or means for fluid reinjection
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
- F05D2270/101—Compressor surge or stall
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- The present disclosure generally relates to compressors, and moreparticularly relates to systems and methods for an axial compressor with a secondary fluid flow to improve at least one of a performance and a stability of the axial compressor.
- Compressors can be used in a variety of applications, and for example, compressors, such as axial compressors, may be part of a gas turbine engine. Generally, compressors include multiple stages, where each stage includes a rotor and a stator. In multistage compressors, there may be a progressive reduction in stage pressure ratio, such that a rear stage develops a lower pressure ratio than a first stage. As the performance of the compressor can be defined by the maximum overall pressure ratio that can be achieved for a given mass flow, the lower pressure ratio in the rear stage may limit the performance and stability of the compressor.
- Accordingly, it is desirable to provide systems and methods for an axial compressor with a secondary fluid flow to improve at least one of a performance and a stability of the axial compressor. Furthermore, other desirable features and characteristics of the present invention will become apparent from the subsequent detailed description and the appended claims, taken in conjunction with the accompanying drawings and the foregoing technical field and background.
- According to various embodiments,a compressor is provided. The compressor comprises a first stage having a first rotor and a first stator and a second stage downstream from the first stage in a direction of a fluid flow. The compressor also comprises a secondary flow system that directs fluid from the second stage into the first stator to improve at least one of a performance and a stability of the compressor.
- A method of improving at least one of a performance and a stability of an axial compressor is provided according to various embodiments. The axial compressor includes a first stage upstream from a second stage in a direction of a main fluid flow. In one embodiment, the method includes receiving a secondary fluid having a first static pressure; and directing the secondary fluid into a first stator of the first stage to disrupt a main fluid flow through the first stator, the main fluid flow through the first stator having a second static pressure that is different than the first static pressure.
- Also provided according to various embodiments is an axial compressor. The axial compressor comprises a first stage having a first rotor and a first stator and a second stage having a second rotor and a second stator. The second stage is downstream from the first stage in a direction of an air flow. The axial compressor also comprises a secondary air flow system that directs air adjacent to the second stator into the first stator to disrupt the air flow through the first stator.
- The exemplary embodiments will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, and wherein:
-
Fig. 1 is a schematic partially cut-away illustration of a gas turbine enginethat includes an axialcompressor with a secondary fluid flow in accordance with various embodiments; -
Fig. 2 is a schematic cross-sectional illustration of the gas turbine engine ofFig. 1 , taken along line 2-2 ofFig. 1 ; -
Fig. 3 is a schematic meridional sectional view through a portion of the axial compressor ofFig. 1 ; -
Fig. 4 is a detail cross-sectional view of a portion of the axialcompressor ofFig. 1 ,as indicated by line 4-4 inFig. 1 ; -
Fig. 5 is a simplified view of the cross-section ofFig. 4 ; -
Fig. 5A is a further cross-sectional view ofFig. 5 , taken alongline 5A-5A ofFig. 5 ; and -
Fig. 6 is a flowchart illustrating an exemplary method for improving at least one of a performance and a stability of the axial compressor. - The following detailed description is merely exemplary in nature and is not intended to limit the application and uses. Furthermore, there is no intention to be bound by any expressed or implied theory presented in the preceding technical field, background, brief summary or the following detailed description.In addition, those skilled in the art will appreciate that embodiments of the present disclosure may be practiced in conjunction with any type of compressor, and that the axial compressor described herein is merely one exemplary embodiment of the present disclosure.It should be noted that many alternative or additional functional relationships or physical connections may be present in an embodiment of the present disclosure.As used herein, the term module refers to any hardware, software, firmware, electronic control component, processing logic, and/or processor device, individually or in any combination, including without limitation: application specific integrated circuit (ASIC), an electronic circuit, a processor (shared, dedicated, or group) and memory that executes one or more software or firmware programs, a combinational logic circuit, and/or other suitable components that provide the described functionality.
- For the sake of brevity, conventional techniques related to signal processing, data transmission, signaling, control, and other functional aspects of the systems (and the individual operating components of the systems) may not be described in detail herein. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent example functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in an embodiment of the present disclosure.
- With reference to
Figs. 1 and2 ,an exemplarygas turbine engine 10is shown, which includes a secondary air flow system according to various embodiments. It should be noted that while the secondary air flow system is discussed herein with regard to agas turbine engine 10, the secondary air flow system can be employed with any suitable engine, such as a turbojet engine, a scramjet engine, an auxiliary power unit (APU), etc. Thus, the following description is merely one exemplary use of the secondary air flow system. In this example, the exemplary gas turbine engine 10includes afan section 12, acompressor section 14, acombustion section 16, aturbine section 18, and anexhaust section 20. As the fan section12, the combustion section16, the turbine section 18and the exhaust section 20can be substantially similar to a fan section, combustion section, turbine section and exhaust section associated with a conventional gas turbine engine, the fan section12, the combustion section16, the turbine section 18and the exhaust section 20will not be discussed in great detail herein. In addition, although the figures shown herein depict an example with certain arrangements of elements, additional intervening elements, devices, features, or components may be present in an actual embodiment. It should also be understood thatFigs. 1 and2 are merely illustrative and may not be drawn to scale. In addition, while the fluid discussed herein is described as air, it should be noted that the various teachings of present disclosure is not so limited, but rather, any suitable fluid can be employed. - The
fan section 12 includes afan 22 mounted in afan casing 24. Thefan 22 induces air from the surrounding environment into the engine and passes a fraction of this air toward thecompressor section 14. Thecompressor section 14 includes at least one compressor and, in this example, includes a low-pressure (LP) compressor 26 (may also be referred to as an intermediate-pressure (IP) compressor, a booster or T-stage) and a high-pressure (HP)compressor 28. TheLP compressor 26 raises the pressure of the air directed into it from the fan 22and directs the compressed air into the HPcompressor 28. The LP compressor 26and the HP compressor 28may be axi-symmetrical about a longitudinal centerline axis C. TheLP compressor 26 and the HPcompressor 28 are mounted in a compressor casing 30 (hereinafter referred to as a shroud 30). - Still referring to
Fig. 2 , thecombustion section 16 ofgas turbine engine 10 includes acombustor 32 in which the high pressure air from the HP compressor 28is mixed with fuel and combusted to generate a combustion mixture of air and fuel. The combustion mixture is then directed into theturbine section 18. Theturbine section 18 includes a number of turbines disposed in axial flow series.Fig. 2 depicts ahigh pressure turbine 34, anintermediate pressure turbine 36, and alow pressure turbine 38. While three turbines are depicted, it is to be understood that any number of turbines may be included according to design specifics. For example, a propulsion gas turbine engine may comprise only a high pressure turbine and a low pressure turbine. The combustion mixture from thecombustion section 16 expands through eachturbine turbines gas turbine engine 10 via concentrically disposed spools orshafts exhaust section 20. - With reference to
Fig. 3 , a schematic meridional sectional viewthrough a portion of the HP compressor 28is shown. In this example, the HP compressor 28includes anaxial compressor section 46 and acentrifugal compressor section 48. Theaxial compressor section 46 includes one ormore rotors 120, one ormore stators 122 and a secondary flow system or secondary air flow system 124 (schematically illustrated by reference numeral 124). The one ormore rotors 120 and the one ormore stators 122 are enclosed by the shroud 30 (Fig. 2 ), and in one example, the secondaryair flow system 124 can also be enclosed by theshroud 30. Theaxial compressor section 46 can also include astrut 126 and an inletguide vane system 128. Thecentrifugal compressor section 48 can include animpeller 130, adiffuser 132 and adeswirlsection 134. Since thestrut 126, inletguide vane system 128,impeller 130,diffuser 132 anddeswirlsection 134 are generally known in the art, they will not be discussed in great detail herein. - With continued reference to
Fig. 3 ,theaxial compressor section 46 includes one or more compressor stages spaced in an axial direction along the longitudinal centerline axis C, with the one ormore rotors 120 and the one ormore stators 122 cooperating to define a stage. In one example, theaxial compressor section 46 comprises a seven stage axial compressor. It should be noted, however, that theaxial compressor section 46 can include any number of stages, and thus, the number of stages illustrated and described herein is merely exemplary. Furthermore, the secondaryair flow system 124 can be employed with anaxial compressor section 46 having any number of stages, and thus, it will be understood that the present teachings herein are not limited to anaxial compressor section 46 having seven stages. - In this example, the one or
more rotors 120includesseven rotors more stators 122 includes sevenstators axial compressor section 46, withrotor 136 andstator 144 formingstage 1,rotor 137 andstator 145 formingstage 2,rotor 138 andstator 146 formingstage 3,rotor 139 andstator 147 formingstage 4,rotor 140 andstator 148 formingstage 5,rotor 141 andstator 149 formingstage 6 androtor 142 andstator 150 formingstage 7. It should be noted that the number of rotors, number of stators and number of stages associated with theaxial compressor section 46 is merely exemplary, as theaxial compressor section 46 can include any number of rotors, stators and stages. In addition, it will be understood that the flow of air through theaxial compressor section 46 is that viewed from the stator frame of reference. - With regard to
Fig. 4 ,stage 6 andstage 7 of theaxial compressor section 46 are shown in greater detail. As will be discussed in greater detail herein, in this example, thestage 6 and stage 7flowfieldof theaxial compressor section 46 cooperate with the secondaryair flow system 124. It should be noted that whilestage 6 andstage 7 are described and illustrated herein as cooperating with the secondaryair flow system 124,stage 1,stage 2,stage 3,stage 4 and/orstage 5 can cooperate with the secondaryair flow system 124, if desired. Thus, the following description and the various teachings of the present disclosure are not limited tostage 6 andstage 7. - With regard to
Fig. 4 , the rotors 141-142 each include adisk 154 and a plurality ofblades 156. Thedisk 154 of each of the rotors 141-142are coupled to theshaft 44 associated with the gas turbine engine 10 (Fig. 2 ). Theshaft 44 rotates each of the rotors 141-142at a desired speed. In this example, thedisk 154 is annular and is coupled to theshaft 44 about abore 160 defined along a central axis of thedisk 154. Thedisks 154 are sized and shaped to cooperate with fore and aft bearings as is generally known, to couple the respective rotor 141-142to theshaft 44 for rotation. Thedisk 154 of each of the rotors 141-142also defines a perimeter orcircumference 162. In this example, theblades 156 are coupled to thecircumference 162 of thedisk 154. Generally, theblades 156 are formed or cast with thedisk 154, however, theblades 156 can be coupled to thedisk 154 through a suitable technique, such as welding, or theindividual blades 156 can be inserted into and retained in slots defined in thedisk 154. - The
blades 156 are coupled to thedisk 154 of each of the rotors 141-142 along thecircumference 162 to turn and acceleratea fluid in the stator frame of reference, such as air, as the fluid moves through or past theblades 156. It should be noted that this particular arrangement of theblades 156 on each of the rotors 141-142 is merely exemplary, as the rotors 141-142can have any desired number and arrangement ofblades 156 to turn and accelerate the fluid as desired. Further, it should be noted that theblades 156 accelerate the fluid from a stationary frame of reference or a stator frame of reference. Theblades 156 of each of the rotors 141-142extend outwardly, radially or in a direction away from the central axis of the rotors 141-142towards a respective one of a sixthstageshroud housing 164 and a seventhstage shroud housing 166. Thus, the sixthstage shroud housing 164 and the seventhstage shroud housing 166 can enclose a respective stage of theaxial compressor section 46. For example, the sixthstage shroud housing 164 can enclose therotor 141 and the stator 149 (stage 6), and the seventhstage shroud housing 166 can enclose therotor 142 and the stator 150 (stage 7). As will be discussed in greater detail below, at least the sixthstageshroud housing 164 cooperates with the secondaryair flow system 124. - With continued reference to
Fig. 4 , the sixthstage shroud housing 164 includes arotor portion 168 and astator portion 170. In one example, therotor portion 168 includes amating extension 172 to couple the sixthstage shroud housing 164 to acorresponding extension 174 of theshroud 30. Therotor portion 168 extends generally in an axial direction relative to the centerline C of the gas turbine engine 10and substantially perpendicular to an axis of theblades 156. Therotor portion 168 generally extends from an area adjacent to theextension 174 of theshroud 30 to an area adjacent to thestator 149, and serves to substantially enclose therotor 141. - The
stator portion 170 is coupled to therotor portion 168 and to thestator 149. In one example, therotor portion 168 can be integrally formed with thestator portion 170; however, therotor portion 168 and thestator portion 170 can comprise discrete components coupled together via a suitable technique, such as welding, mechanical fasteners, etc., if desired. Thestator portion 170 substantially extends from therotor portion 168 to aterminal end 176. Generally, theterminal end 176 of thestator portion 170 lies in the same plane as an end 178 of thestator 149. In this example, theterminal end 176 of thestator portion 170 is spaced a distance apart or away from the seventhstage shroud housing 166, however, the sixthstage shroud housing 164 and seventhstage shroud housing 166 can be coupled together, if desired. - The
stator portion 170 defines aplenum 180. Theplenum 180 is in communication with the secondaryair flow system 124, as will be discussed further herein. In one example, theplenum 180 includes afirst side 182, asecond side 184 and athird side 186, which cooperate to define a chamber over thestator 149. It should be noted that the shape and number of sides associated with theplenum 180 is merely exemplary, as theplenum 180 can have any desired shape to facilitate a secondary air flow through thestator 149. In addition, it should be noted that the use of theplenum 180 is merely exemplary. For example, a secondary air flow can be introduced into thestator 149 via any suitable technique, such as the use of a strut, tube or a pipe that directs a secondary air flow into thestator 149. Thus, the secondary air flow need not be directed into one or moreinterior passages 191 of thestator 149, as discussed further herein. Further, the secondary air flow need not be directed into thestator 149. Rather, the secondary air flow can be directed in front of thestator 149, in a direction substantially perpendicular to the main gas path air flow M to disrupt the flow of air through thestator 149. - In this example, the
first side 182 of theplenum 180 defines at least one conduit ortube188, which is in communication with a portion of the secondary air flow system 124to receiveair from the secondaryair flow system 124. In one example, thefirst side 182 can include two to fourtubes 188 spaced apart along a perimeter or circumference of thefirst side 182, however, it will be understood that thefirst side 182 can include any number oftubes 188, such as asingle tube 188, in communication with the secondaryair flow system 124. In addition, it should be noted that while thetube 188 is illustrated herein as being defined near a middle of thefirst side 182, thetube 188 can be defined through thesecond side 184, if desired. Thus, the location of thetube 188 relative to theplenum 180 illustrated herein is merely exemplary. - The
first side 182 is coupled to thesecond side 184 and thethird side 186. Thesecond side 184 is adjacent to therotor portion 168 and is coupled to thethird side 186. Thethird side 186 defines one ormore openings 190 through which air from theplenum 180 can flow into one or moreinterior passages 191 in the stator 149.In one example, the one ormore openings 190 are substantially cylindrical, however, the one ormore openings 190 can have any desired geometrical shape, such as rectangular, etc. Generally, thethird side 186 can define about oneopening 190 to about a number ofopenings 190 equal to a number ofinterior passages 191 defined in thestator 149 around a perimeter or a circumference of thethird side 186 to enable air from theplenum 180 to enter the one or moreinterior passages 191 of thestator 149. It should be noted that the number ofopenings 190 is merely exemplary, as thethird side 188 can have any number ofopenings 190 based on the desired secondary air flow into thestator 149. Thethird side 188 can be coupled to thestator 149. - The seventh
stage shroud housing 166 includes arotor portion 192 and astator portion 194. In one example, therotor portion 192 includes amating extension 196 to couple the seventhstage shroud housing 166 to thecorresponding extension 174 of theshroud 30. Therotor portion 192 extends generally in an axial direction relativeto the centerline C of thegas turbine engine 10 and substantially perpendicular to an axis of theblades 156. Therotor portion 192 generally extends from an area adjacent to theextension 174 of theshroud 30 to an area adjacent to thestator 150, and serves to substantially enclose therotor 142. - The
stator portion 194 is coupled to therotor portion 192 and to thestator 150. In one example, therotor portion 192 can be integrally formed with thestator portion 194; however, therotor portion 192 and thestator portion 194 can comprise discrete components coupled together via a suitable technique, such as welding, mechanical fasteners, etc. Thestator portion 194 substantially extends from therotor portion 192 to aterminal end 197. In this example, theterminal end 197 of thestator portion 194 extends outwardly or along an axis substantially transverse to a longitudinal axis of thestator portion 194. - With continued reference to
Fig. 4 , the stator 149is positioned between therotor 141 and therotor 142, and is coupled to thestator portion 170 of the sixthstage shroud housing 164. Generally, thestator 149 is positioned between therotor 141 and therotor 142 such that afirst gap 198 is defined between thestator 149 and therotor 141 and asecond gap 200 is defined between thestator 149 and therotor 142. It should be noted that thefirst gap 198 betweenrotor 141 and thestator 149 need not be the same size or dimension as thesecond gap 200 between therotor 142 and thestator 149. Thefirst gap 198 facilitates the movement of therotor 141 relative to thestator 149, and thesecond gap 200 facilitates the movement of therotor 142 relative to thestator 149. As will be discussed, thefirst gap 198 also enables a secondary air flow through thestator 149 to exit into a main gas path air flow M (Fig. 3 ). - The
stator 149 is fixed or stationary relative to the rotors 141-142, and does not move or rotate with theshaft 44. Thestator 149 includes a hub202, one or more vanes204and in this example, thestator 149 is positioned above a rotating sea1206. In one example, thehub 202 and the one ormore vanes 204 can be integrally formed together, via a suitable casting process, but one or more of thehub 202 and the one ormore vanes 204 can be formed as discrete components and coupled together through a suitable technique, such as welding, for example. Thehub 202 can be substantially annular, and can comprise a ring. Thehub 202 includes a perimeter orcircumference 208, and one ormore openings 210 can be defined through thecircumference 208. - As will be discussed, the one or
more openings 210 enable air from the secondaryair flow system 124 to flow through one or moreinterior passages 191 in thestator 149 and into ahub cavity 213 defined between thehub 202 and therotating seal 206. It should be noted that thehub cavity 213 need not be defined by a rotating seal, and that a hub cavity can be defined by thehub 202 itself. Thus, the use of therotating seal 206 is merely exemplary. Generally, theinterior passages 191 in thestator 149 are defined through one or more of thevanes 204. Stated another way, one or more of thevanes 204 of thestator 149 defines aninterior passage 191. In one example, theinterior passage 191 extends from anend 204a of thevane 204 adjacent to theopening 190 to anend 204b of thevane 204 adjacent to therotating seal 206. It should be noted that while a singleinterior passage 191 is illustrated herein, thestator 149 can include any number ofinterior passages 191, from one to about the number ofvanes 204 associated with thestator 149. Furthermore, the number ofinterior passages 191 need not be equal to the number ofopenings 190, if desired. - The air from the secondary
air flow system 124 flows through theinterior passages 191, into ahub cavity 213, or the area defined between thehub 202 and therotating seal 206. In one example, the one ormore openings 210 are substantially cylindrical, however, the one ormore openings 210 can have any desired geometrical shape, such as rectangular, etc. Generally, the one ormore openings 210 are defined through thecircumference 208 such that a respective one of theopenings 210 is aligned with a respective one of the interior passages191 to ensure air flow through thehub 202 into thehub cavity 213. Generally, thecircumference 208 can define about one to about a number of openings 210about equal to the number ofvanes 204 to enable air from thestator 149 to enter thehub cavity 213. It should be noted that the number ofopenings 210 is merely exemplary, as thecircumference 208 can have any number ofopenings 210 based on the desired air flow through thestator 149. Furthermore, as discussed previously, the secondary air flow can be introduced into thehub 202 of thestator 149 via any suitable technique, and thus, the secondary air flow need not be directed into one ormore vanes 204 of thestator 149. - The
vanes 204 are coupled to thecircumference 208 of the hub 202and thestator portion 170 of the sixthstage shroud housing 164 at afirst end 149b of thestator 149. It should be noted that while thestator 149 is described herein as being coupled to the sixthstage shroud housing 164 at thefirst end 149b, thestator 149 can be coupled to theaxial compressor section 46 so as to be fixed via any suitable technique. Thevanes 204 are coupled to thehub 202 of thestator 149 along thecircumference 208. Thevanes 204 increase the static pressure of the air and direct or guide the air as the air moves through thevanes 204. It should be noted that this particular arrangement of thevanes 204 on thestator 149 is merely exemplary, as thestator 149 can have any desired number and arrangement ofvanes 204 to increase the static pressure of the air and direct or guide the air as desired. As discussed, one or more of thevanes 204 can include theinterior passage 191. Theinterior passage 191 permits a secondary air flow through thestator 149, as will be discussed in greater detail herein. - The
rotating seal 206 can be coupled to thedisk 154 of therotor 141 adjacent to thecircumference 162 of therotor 141. It should be noted that the coupling of therotating seal 206 to therotor 141 is merely exemplary. In one example, therotating seal 206 is coupled to therotor 141 so as to be disposed a distance D away from thehub 202 of thestator 149 or from asecond end 149c of thestator 149. With reference toFigs. 4 and5 , therotating seal 206 serves to reduce a leakage of air around thestator 149. Therotating seal 206 also redirects and controls the amount of the air from an exit of thestator 149 toward a front orfirst side 149a of thestator 149. In this regard, in one example, therotating seal 206 includes at least oneseal 212. In this example, therotating seal 206 includes threeseals 212, which serve to substantially restrict a flow of air towards therotor 142. Stated another way, theseals 212 substantially control the amount of the air flow from thestator 149 towards the first side149a of thestator 149 to reduce fluid leakage around thehub 202 of thestator 149. - With continued reference to
Fig. 4 , thestator 150 is positioned adjacent to therotor 142, and is coupled to thestator portion 194 of the seventhstage shroud housing 166. Generally, thestator 150 is positioned adjacent to therotor 142 such that athird gap 214 is defined between thestator 150 and therotor 142. Thethird gap 214 allows the movement of therotor 142 relative to the stator 150.Thestator 150 is fixed or stationary relative to therotor 142, and does not move or rotate with theshaft 44. Thestator 150 includes a hub216 and one ormore vanes 218. In one example, thehub 216 and the one ormore vanes 218 can be integrally formed together, via a suitable casting process, but one or more of thehub 216 and the one ormore vanes 218 can be formed as discrete components and coupled together through a suitable technique, such as welding, for example. - The
hub 216 can be substantially annular, and can comprise a ring. Thehub 216 includes a perimeter orcircumference 222. Thevanes 218 are coupled to thecircumference 222 of thehub 216 and thestator portion 194 of the seventhstage shroud housing 166. It should be noted that while thestator 150 is described herein as being coupled to the seventhstage shroud housing 166, thestator 150 can be coupled to theaxial compressor section 46 so as to be fixed or stationary relative to therotor 142 via any suitable technique. Thevanes 218 are coupled to thehub 216 of the stator 150along thecircumference 222. Thevanes 218 increase the static pressure of the air and direct or guide the air as the air moves through thevanes 218. It should be noted that this particular arrangement of thevanes 218 on thestator 150 is merely exemplary, as thestator 150 can have any desired number and arrangement ofvanes 218 to increase the static pressure of the air and direct or guide the air as desired. - With reference to
Fig. 3 , the secondaryair flow system 124 directs air from a higher static pressure stage of theaxial compressor section 46 into lower static pressure stage of theaxial compressor section 46. In this regard, the static pressure of the air in theaxial compressor section 46 increases with each stage of the axial compressor section 46 (i.e. the static air pressure increases as the air flows downstream). Thus, the air instage 2 has a higher static pressure than the air instage 1, the air instage 3 has a higher static pressure than the air instage 2 andstage 1, the air instage 4 has a higherstatic pressure than the air in stage 3-1, the air instage 5 has a higherstatic pressure than the air in stages 4-1, the air instage 6 has a higherstatic pressure than the air in stages 5-1 and the air instage 7 has a higherstatic pressure than the air in stages 6-1. By injecting higher static pressure air into a lower static pressureair flow at the hub of the respective stator 144-149, the hub air flow in the lower static pressure stator 144-149 is disrupted, which causes the main gas path air flow Mor the air flowing through the stator 144-149 from an upstream rotor 136-141to be directed towards the terminal ends or tips of the respective blades of the respective rotor 138-142 of the adjacent stage.In this example, the secondaryair flow system 124 will be described herein as directing higher static pressure air fromstage 7 into thestator 149 of lowerstatic pressure stage 6. It should be understood that this particular example of the secondaryair flow system 124 is merely exemplary, as the teachings of the secondaryair flow system 124 can be applied or used to direct downstream air to any desired upstream stator 144-149 to disrupt or destabilize the flow of air through the hub of the respective upstream stator 144-149. - For example, the secondary
air flow system 124 can direct air fromstage 7 into thestator 149 ofstage 6, thestator 148 ofstage 5, thestator 147 ofstage 4, thestator 146 ofstage 3, thestator 145 ofstage 2 and/or thestator 144 ofstage 1. The secondaryair flow system 124 can also direct air fromstage 6 into the stators148 ofstage 5, thestator 147 ofstage 4, thestator 146 ofstage 3, thestator 145 ofstage 2 and/or thestator 144 ofstage 1. Further, the secondaryair flow system 124 can direct air fromstage 5 to thestator 147 ofstage 4,thestator 146 ofstage 3, thestator 145 ofstage 2 and/or thestator 144 ofstage 1. Similarly, the secondaryair flow system 124 can direct air fromstage 4 to thestator 146 ofstage 3, thestator 145 ofstage 2 and/or thestator 144 ofstage 1. The secondaryair flow system 124 can also direct air fromstage 3 to thestator 145 ofstage 2 and/or thestator 144 ofstage 1. The secondaryair flow system 124 can also direct air fromstage 2 to thestator 144 ofstage 1. Thus, the following description is merely an exemplary embodiment for the secondary air flow system 124.Moreover, while a single secondaryair flow system 124 is described herein as directing fluid from a single high static pressure stage to a single low static pressure stage, the secondaryair flow system 124 can direct air from a single high static pressure stage to multiple low static pressure stages. Thus, the secondaryair flow system 124 is not limited to directing downstream fluid from a stage of the axial compressor section 46to a single stage of the axial compressor section 46upstream. Furthermore, the secondaryair flow system 124 is not limited to directing air from a downstream stage to an adjacent upstream stage. Rather, the secondaryair flow system 124 can direct higher static pressure air to any lower staticpressure air stator - Furthermore, the secondary
air flow system 124 need not direct air from a stage of theaxial compressor section 46 to an upstream stage of theaxial compressor section 46. Rather, with reference toFig. 5 , the secondaryair flow system 124 can comprise a remote orexternal source 234 of higher static pressure air, which can be injected into a respective one of the stators 144-148.Theexternal source 234 is illustrated schematically inFigs. 4 and5 as being outside of theshroud 30, and thus, remote from theHP compressor section 28. It will be understood, however, that theexternal source 234 can comprise a source of air external to thegas turbine engine 10 itself,and thus, the location of theexternal source 234 inFigs. 4 and5 is merely exemplary. Theexternal source 234 can be in communication with thetube 188 through any suitable device, such as a tube, strut, etc. to introduce the higher static pressure air into theplenum 180. - In addition, it should be understood that the secondary
air flow system 124 can include avalve 230 to control the flow of the air through the tubel88. Generally, thevalve 230 can comprise any suitable mechanical or electro-mechanical device that is movable between an opened position to allow the flow of air through thetube 188 and a closed position to prevent the flow of air through thetube 188, and various positions therebetween, if desired, as known to those skilled in the art. In one example, thevalve 230 can be disposed in thetube 188, however, thevalve 230 can be positioned at any desired location to control the flow of air into theplenum 180. Further, thevalve 230 can be in communication with acontrol module 232, which is illustrated schematically inFigs. 4 and5 . Thecontrol module 232 can be associated with or part of an engine control module for thegas turbine engine 10, and thus, it should be noted that the location of thecontrol module 232 inFigs. 4 and5 is merely exemplary. Based on the receipt of sensor data measured and observed by one or more sensors associated with theaxial compressor section 46 and/or thegas turbine engine 10, input from other modules associated with thegas turbine engine 10 or upon the receipt of user input, thecontrol module 232 can output the one or more control signals to thevalve 230 to move thevalve 230 between the opened position and the closed position. Thus, the secondaryair flow system 124 can be controlled via thecontrol module 232 and thevalve 230 based on the requirements of thegas turbine engine 10. It should be noted that the use of thevalve 230 is merely exemplary, as the secondaryair flow system 124 can be a passive system or can always be in operation (i.e. not controlled by a valve 230) so long as downstream higher static pressure air is available for use by the secondaryair flow system 124. - In the example of
Fig. 4 , the secondaryair flow system 124 directs fluid into thestator 148 to disrupt the hub flow of air through thestator 148, which in turn causes the air to flow towards an outboard region, a terminal end ortip 156a of theblades 156 of therotor 142, thereby decreasing the pressure gradient at thetip 156a of therotor 142 and improving the range of therotor 142 to stall. In this example, the secondaryair flow system 124 includes aplenum 224. It should be noted that the use of theplenum 224 is merely exemplary, as the secondaryair flow system 124 can include any suitable passage or conduit for directing a secondary air flow into thetube 188. Theplenum 224 is defined by therotor portion 192 and thestator portion 194 of the seventhstage shroud housing 166, and a portion of theshroud 30. For ease of understanding, theplenum 224 is illustrated inFig. 4 in broken lines, however, it will be understood that theplenum 224 is defined by the structure of the seventhstage shroud housing 166 and a portion of the shroud 30.Theplenum 224 is disposed adjacent to thestator 150 to receive a portion of the air exiting thestator 150, which enters into theplenum 224 at a portion of theplenum 224 generally identified as228. - In this example, as air enters the
axial compressor section 46 from the fan section 12 (Fig. 2 ), with reference toFig. 3 , the air flows through the inletguide vane system 128 and is turned and accelerated by therotor 136 in the stator frame of reference. The air exiting therotor 136 enters thestator 144, and thestator 144 increases the static pressure of the air and directs the air into therotor 137. From therotor 137, thestator 145 further increases the static pressure of the air and directs the air into therotor 138. Therotor 138 further turns and accelerates the air, and the air enters thestator 146. Thestator 146 further increases the static pressure of the air, which is guided into therotor 139. Therotor 139 further turns and accelerates the air, and the air enters thestator 147. Thestator 147 increases the static pressure of the air, which is guided into therotor 140. From therotor 140, the air flows into thestator 148. Thestator 148 increases the static pressure of the air and guides the air into therotor 141. - With reference to
Figs. 4 and5 , the air turned and accelerated by therotor 141 enters thestator 149 in a direction substantially perpendicular to a longitudinal axis L of thevanes 204. Provided that air is available downstream, air enters theplenum 224 of the secondaryair flow system 124 and flows through theplenum 224 to theplenum 180. As the air exiting thestator 150 has a high static pressure, the air naturally flows into theplenum 224 without requiring additional features, such as a pump or flow guides, for example. The air from theplenum 180 exits the one ormore openings 190 into thestator 149, flows through theinterior passages 191 and exits into thehub cavity 213 via the one ormore openings 210 in thehub 202. Thus, the secondaryair flow system 124 directs higher static pressure air into thehub 202 of thestator 149. From thehub cavity 213, the air flows through the first gap 198 (Fig. 4 ), and back into thestator 149 flowfield near thefirst side 149a of thestator 149 where the flow of the main gas path air flow M is intentionally disrupted. - With reference to
Figs. 5 and5A , a simplified view ofFig. 4 is shown. InFigs. 5 and5A , the rotors 141-142 have been removed to more clearly show the secondary air flow path through the secondaryair flow system 124 into thehub 202 of thestator 149. As shown inFigs. 5 and5A , the air from theplenum 180 flows down through thestator 149, substantially parallel to the longitudinal axis L of thestator 149, and exits into thehub cavity 213 via the one ormore openings 210. From thehub cavity 213, the air flows through the first gap 198 (Fig. 4 ), and back into the stator 149flowfield near the first side149a of thestator 149 where the flow of the main gas path air flow M is intentionally disrupted. - With reference to
Fig. 4 , from the first side149a of thestator 149, the air is directed through thestator 149 into the rotor 142and is displaced outward towards the outboard region and thetips 156a of theblades 156. Therotor 142 turns and accelerates the air, which enters thestator 150. Thestator 150 further increases the static pressure of the air, and directs the air into the impeller 130 (Fig. 3 ). A portion of the air from thestator 150 also enters the plenum224 at 228. - The secondary
air flow system 124 decreases the pressure gradient acting on the outboard region and thetips 156a of theblades 156 of therotor 142 by disrupting the air flow at thehub 202 of thestator 149 and moving the air flow in thestator 149 towards the outboard region and thetips 156a of theblades 156. By disrupting the hub air flow through thestator 149, the margin to stall of therotor 142 is improved. In one example, the margin to stall of therotor 142 is increased by about 3.0 percent (%) based on an increased flow of 1.0 percent (%) through thestator 149 from the secondaryair flow system 124. The increased margin to stall of therotor 142 raises the pressure ratiothat can be achieved for a given mass flow atstage 7 of theaxial compressor section 46, thereby improving at least one of the performance and the stability of theaxial compressor section 46. - Thus, according to various embodiments, with reference to
Fig. 6 and continuing reference toFigs. 1-6 , a method for improving at least one of theperformanceand the stability of theaxial compressor section 46 is provided. It should be noted that as used herein, the term "stability" means the stall margin or stall line of the compressor. Thus, the method described and illustrated herein improves the stall margin or stall line of theaxial compressor section 46. In one example, the method starts at 300. At 302, the method receives a secondary fluid, such as air, having a first static pressure. For example, the air is from a downstream stage, such asstage 2,stage 3,stage 4,stage 5,stage 6 orstage 7 of theaxial compressor section 46 and has a higher static pressure. At 304, the method directs the secondary fluid, such as air, into thestator 144, 145,146, 147,148, 149 associated with an upstream stage (i.e.stage 1,stage 2,stage 3,stage 4,stage 5, stage 6) to disrupt a main fluid flow through thestator stator upstream stator stator stage 1,stage 2,stage 3,stage 4,stage 5, stage 6) to disrupt a main gas path air flow M through a hub of thestator stator 149 at any suitable position or location to disrupt the main gas path air flow M through thestator 149, such as by directing secondary fluid into thestator 149 near thefirst side 149a of thestator 149, near thefirst end 149b of thestator 149 or through theinterior passages 191, through thehub 202 into thehub cavity 213. Thus, directing the secondary fluid into thestator 149 does not necessarily require the secondary fluid flow directly into thestator 149, but the secondary fluid flow can be directed at thefirst side 149a of thestator 149 such that the secondary fluid flow disrupts the main gas path air flow M through thestator 149. By disrupting the main gas path air flow M through theupstream stator - It should be noted that while the secondary
air flow system 124 has been described and illustrated herein for improving the performance and/or the stability of theaxial compressor section 46, the present teachings of this disclosure can be applied to other portions of thegas turbine engine 10 to improve a performance and/or a stability. For example, with reference toFig. 2 , a secondary air flow of downstream air, such as air from theHP compressor 28, can be directed upstream into thefan 22. The secondary air flow can be introduced into thefan 22 via any suitable technique, such as a bore, tube, strut, etc. As a further example, with continued reference toFig. 2 , a secondary air flow of downstream air, such as air from theHP compressor 28, can be directed upstream into theLP compressor 26. The secondary air flow can be introduced into theLP compressor 26 via any suitable technique, such as a bore, tube, strut, etc. - In this document, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Numerical ordinals such as "first," "second,""third," etc. simply denote different singles of a plurality and do not imply any order or sequence unless specifically defined by the claim language. The sequence of the text in any of the claims does not imply that process steps must be performed in a temporal or logical order according to such sequence unless it is specifically defined by the language of the claim. The process steps may be interchanged in any order without departing from the scope of the invention as long as such an interchange does not contradict the claim language and is not logically nonsensical.
- While at least one exemplary embodiment has been presented in the foregoing detailed description, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the disclosure in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing the exemplary embodiment or exemplary embodiments. It should be understood that various changes can be made in the function and arrangement of elements without departing from the scope of the disclosure as set forth in the appended claims and the legal equivalents thereof.
Claims (14)
- A compressor, comprising:A first stage having a first rotor and a first stator;A second stage downstream from the first stage in a direction of a fluid flow; andA secondary flow system that directs fluid from the second stage into the first stator to improve at least one of a performance and a stability of the compressor.
- The compressor of claim 1, further comprising:A first shroud housing positioned adjacent to the first stage, the first stator coupled to the first shroud housing and the first shroud housing defining a plenum over the first stator, with the plenum in communication with the secondary flow system and the first stator to direct the fluid into the first stator.
- The compressor of claim 2, wherein the secondary flow system directs fluid from the second stage into a hub of the first stator.
- The compressor of claim 2, wherein the plenum includes at least one tube in communication with the secondary flow system and at least one opening in communication with the first stator to direct fluid from the secondary flow system into the first stator.
- The compressor of claim 4, wherein the first stator has at least one vane extending along a longitudinal axis, and the at least one vane includes a passage in communication with the at least one opening to receive the fluid from the secondary flow system.
- The compressor of claim 1, wherein the first stator includes a first end, a second end and a first side, and the fluid from the secondary flow system enters the first stator at the first end, exits the first stator at the second end and is redirected into the first side of the first stator to disrupt the fluid flow through the first stator.
- The compressor of claim 6, wherein the first stator includes a hub at the second end that defines a hub cavity, and the hub includes one or more openings in communication with the hub cavity.
- The compressor of claim 1, wherein the second stage includes a second rotor and a second stator, and the secondary flow system is defined as a second plenum having a first end in communication with the first stator and a second end in communication with the second stator.
- A method of improving at least one of a performance and a stability of an axial compressor, the axial compressor including a first stage upstream from a second stage in a direction of a main fluid flow, the method comprising:Receiving a secondary fluid having a first static pressure; andDirecting the secondary fluid into a first stator of the first stage to disrupt a main fluid flow through the first stator, the main fluid flow through the first stator having a second static pressure that is different than the first static pressure.
- The method of claim 9, wherein receiving the secondary fluid having a first static pressure further comprises:Receiving the secondary fluid from a second stage.
- The method of claim 9, wherein receiving the secondary fluid having a first static pressure further comprises:Receiving the secondary fluid from a source remote from the axial compressor.
- The method of claim 9, wherein directing the fluid into the first stator further comprises:Directing the fluid into the first stator such that the fluid flows through a passage defined in a vane associated with the first stator.
- The method of claim 9, wherein directing the fluid into the first stator further comprises:Directing the fluid into the first stator such that the fluid flows from a first end of the first stator and exits into a hub cavity defined adjacent to a second end of the first stator.
- The method of claim 13, further comprising:Directing the fluid exiting the second end of the first stator towards a first side of the first stator.
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US14/632,024 US10330121B2 (en) | 2015-02-26 | 2015-02-26 | Systems and methods for axial compressor with secondary flow |
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US11814988B2 (en) | 2020-09-22 | 2023-11-14 | General Electric Company | Turbomachine and system for compressor operation |
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DE102016119916A1 (en) * | 2016-10-19 | 2018-04-19 | Ebm-Papst Mulfingen Gmbh & Co. Kg | Fan with fan wheel and stator |
US11098730B2 (en) | 2019-04-12 | 2021-08-24 | Rolls-Royce Corporation | Deswirler assembly for a centrifugal compressor |
US11441516B2 (en) | 2020-07-14 | 2022-09-13 | Rolls-Royce North American Technologies Inc. | Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features |
US11286952B2 (en) | 2020-07-14 | 2022-03-29 | Rolls-Royce Corporation | Diffusion system configured for use with centrifugal compressor |
US11578654B2 (en) | 2020-07-29 | 2023-02-14 | Rolls-Royce North American Technologies Inc. | Centrifical compressor assembly for a gas turbine engine |
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US10330121B2 (en) | 2019-06-25 |
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